Fuel supply system for supplying fuel to a combustion section of a gas turbine

Abstract

A fuel supply system supplies fuel to a plurality of combustion sectors of a combustion section of a gas turbine. Each of the combustion sectors includes at least two combustors. The fuel supply system generally includes a fuel distribution manifold that is in fluid communication with a fuel supply. A first flow path is defined between the fuel distribution manifold and a first combustion sector. A second flow path is defined between the fuel distribution manifold and a second combustion sector.

What is claimed is: 
     
         1 . A system for supplying fuel to a combustion section of a gas turbine, the combustion section having a plurality of combustion sectors, each combustion sector having at least two combustors, the system comprising:
 a. a fuel distribution manifold in fluid communication with a fuel supply;   b. a first flow path defined between the fuel distribution manifold and a first combustion sector; and   c. a second flow path defined between the fuel distribution manifold and a second combustion sector.   
     
     
         2 . The system as in  claim 1 , wherein each of the combustors of the plurality of combustion sectors includes a primary and a secondary fuel circuit. 
     
     
         3 . The fuel supply system as in  claim 2 , wherein the first flow path is in fluid communication with the primary fuel circuit of each combustor of the first combustion sector. 
     
     
         4 . The system as in  claim 2 , wherein the second flow path is in fluid communication with the primary fuel circuit of each combustor of the second combustion sector. 
     
     
         5 . The system as in  claim 1 , further comprising a first and a second flow distribution valve, the first distribution valve being in fluid communication with the fuel distribution manifold and the first combustion sector, and the second flow distribution valve being in fluid communication with the fuel distribution manifold and the second combustion sector. 
     
     
         6 . The system as in  claim 5 , wherein the first flow distribution valve further defines the first flow path between the fuel distribution manifold and each combustor of the first combustion sector. 
     
     
         7 . The system as in  claim 5 , wherein the second flow distribution valve further defines the flow path between the fuel distribution manifold and each combustor of the second combustion sector. 
     
     
         8 . The system as in  claim 5 , further comprising a controller linked to at least one sensor and to the first and the second flow distribution valves, the sensor being configured to sense at least one operating parameter of the gas turbine, the controller selectively operating at least one of the first or the second flow distribution valves based upon the operating parameter sensed by the at least one sensor. 
     
     
         9 . The system as in  claim 8 , wherein the at least one sensor is at least one of an exhaust temperature sensor, a dynamic pressure sensor, an ambient air temperature sensor or a combination of sensors including at least one of the foregoing. 
     
     
         10 . A system for a combustion section of a gas turbine, the combustion section having a plurality of fuel injectors circumferentially spaced within an annular ring enclosed within the combustion section, the fuel supply system comprising:
 a. a fuel distribution manifold in fluid communication with a fuel supply;   b. a first combustion sector in fluid communication with the fuel distribution manifold through a first flow path, the first combustion sector having at least two of the fuel injectors; and   c. a second combustion sector in fluid communication with the fuel distribution manifold through a second flow path, the second fuel injection sector having at least two of the plurality of fuel injectors.   
     
     
         11 . The system as in  claim 10 , wherein each of the at least two fuel injectors of the first and the second fuel injection sectors includes a primary and a secondary fuel circuit. 
     
     
         12 . The system as in  claim 11 , wherein the primary fuel circuit of each fuel injector of the first and the second combustion sectors is in fluid communication with the fuel distribution manifold. 
     
     
         13 . The system as in  claim 11 , further comprising a first and a second flow distribution valve, the first flow distribution valve further defining the first flow path between the fuel manifold and the first fuel injection sector, and the second flow distribution valve further defining the second flow path between the fuel manifold and the second fuel injection sector. 
     
     
         14 . The system as in  claim 13 , wherein the first flow distribution valve is in fluid communication with the primary fuel circuit of each fuel injector of the first fuel injection sector, and the second flow distribution valve is in fluid communication with the primary fuel circuit of each fuel injector of the second combustion sector. 
     
     
         15 . The system as in  claim 13 , further comprising a controller linked to at least one sensor and to the first and the second flow distribution valves, the sensor being configured to sense at least one operating parameter of the gas turbine, the controller selectively operating at least one of the first or the second flow distribution valves based upon the operating parameter sensed by the at least one sensor. 
     
     
         16 . A combustion section of a gas turbine, comprising:
 a. a plurality of combustion sectors arranged circumferentially around an outer casing of the combustion section, each combustion sector having at least two combustors;   b. a fuel distribution manifold at least partially circumferentially surrounding the combustion section, the fuel distribution manifold being in fluid communication with a fuel supply;   c. a first flow path defined between the fuel distribution manifold and a first combustion sector; and   d. a second flow path defined between the fuel distribution manifold and a second combustion sector.   
     
     
         17 . The combustion section as in  claim 15 , wherein each combustor of the plurality of combustion sectors includes a primary and a secondary fuel circuit. 
     
     
         18 . The combustion section as in  claim 16 , wherein the first flow path is in fluid communication with the primary fuel circuit of each combustor of the first combustion sector, and the second flow path is in fluid communication with the primary fuel circuit of each combustor of the second combustion sector. 
     
     
         19 . The combustion section as in  claim 15 , further comprising a first and a second flow distribution valve, the first flow distribution valve further defining the first flow path, and the second flow distribution valve further defining the second flow path. 
     
     
         20 . The combustion section as in  claim 19 , further comprising a controller linked to at least one sensor and to the first and the second flow distribution valves, the sensor being configured to sense at least one operating parameter of the gas turbine, the controller selectively operating at least one of the first or the second flow distribution valves based upon the operating parameter sensed by the at least one sensor.